Aeronautical safety device.



s L VAN METER, Jn AERONAUTICM. SAFETY DEVICE. APPLICATION men gums. ma.

Patented July 25, 1916.

5 SNEETSSHEET l ammo S. L. VAN METER, In.

AERONAUTICAL SAFETY DEVICE. APPLICATION FILED AUG. 8. I913.

1 1 92,480. Patented July 25, 1916.

5 SHEETS-SHEET Z.

idzfm. 3% 4 V s. L. VAN METER, 1B. AERONAUTICAI. SAFETY D EVICE.APPLICATION FILED Mil-1.8. l9l3. 1 1 92,480, Patented July 25, 1916.

s snsns-snzzfs.

awe/.76 2 35 C M, K

S. L. VAN METER, Jn. AERONAUTICAI. SAFETY owes.-

APPUCATl-ON FILED AUG. 3. IQI3. 1 1 92,480. Patented July 25, 1916.

5 SHEETS-SHEET 4.

S. L. VAN METER, In. AERONAUTICAL SAFETY DEVICE.

APPLICATION min nus, m3.

5 $HEETSSIIEET 5- 4 iz: 2 75 o h 6 F929. u I I I WI parachute is -Fig. 9is a detail SOLOMON LEE VAR "marlin, 3a., or LExI'nGToN, xmn'ucmr.

AERONAUTIQAL SAFETY DEVICE.

Specification of Letters Patent.

Patented July 25, 1916.

Application filed August 8, 1918. Serial No. 788,729.

To all whom it may concern:

Be it known that I SOLOMON L. VAN METER, Jr., a citizen 0% the UnitedStates, residing at Lexington, Fayette county, and State of Kentucky,have invented and discovered certain new and useful Improvements inAeronautical Safety Devices, of which the following is a specification.

My invention relates to parachute attachments for aeroplanes and itsobjects are to provide means which shall cally cast into the to the bodyof the aviator on the release of the actuating mechanism, to provideeffective power means for eil'ecting the above action, to provide meansfor insuring the prompt opening of the parachute when thus thrown intothe air, to provide means for lessening the shock imparted to the bodyof the aviator when the parachute has caught the air, to provide meansfor inclosing parachute when it is mounted upon the aeroplane inconnection with means for holding such inclosing means in closedposition and for immediately releasing the same when the discharged fromthe aeroplane, to provide means for holding the operator in his seat andmeans for guarding the aviator against contact with the aeroplane as eis separated therefrom by the separation of the parachute and theaeroplane and generally to improve the construction of a device of thisclams With these ends in view, my invention is embodied in preferableform in the device hereinafter described and illustrated in theaccompanying drawin In these drawings, in elevation of an acre laneshowing my device applied thereto; F1g.,2 is a section on line 22 ofFig. 1; Fig. 3 is a section on line 3-3 of Fig. 1; Fig. 4 is a to planview; Fig. 5 is a section, partly bro en away on line 5-5 of Fig. 6;Fig. 6 is a central section through the inclosing hood for theparachute; Fig. 7 is a detail of the inclosing hood; Fig. 8 is a detailsection of the parachute expanding spring; plan view of part of thereleasing means for the Fig. 10 is a rear view in elevation of the backof the seat and rope attaching member; Fig. 11 is an edge view of thepart shown in Fig. 10; Fig. 12 is a perspective view of the attachingback plate and harness; Flg. 13 is a detail section on line 1313 of Fig.10; Fig. .4. is a side view showing the parachutein act to automatiair aparachute attached the Flgure 1 is a side view perspective of part pult,'is' adapted power mechanism;

active position; Fi .15, a front view in elememben for the aviator;

vation of the guar Fig. 16 is a detail of the frame and is a side viewin e vertical section of a part ower mechanism; Fig. 17 evation, partlyin section, of the upper rear end of the power mechanism; F1 18 is adetail view of the lower part of t e power mechanism; Fig. 191s a sideview in elevation, showing the device just after the arachute has beencast oil from the aerop ane; Fig. 20 is a detail top plan view of partof the parachute expanding spring, after the expanded; Fig. 21 is a online 21 -21 of Fig; plan of part of the aviator; Fig. 23 is a 23 23 ofFig. 22; Fig. 24 is a detail section on line 24 -24.- of Fig. 22; Fig.25 is a side elevation, partly in section of a modified form of thepower means illustrated in Fig. 1; Fig. 26 is a horizontal detailsection on line 26-26 of Fig. 25; Fig. 27 a side view in elevation ofanother modi ed form of power means for casting the lparachute; Fig. 28is an enlarged view part y in section of the device shown in Fig. 27;Fig. 29 is an enlarged detail view of the lower part of Fig.28 and Fig.30 is a detail cross section on line 3030 of Fig. 28.

Referring to the drawings, 1 is an aeroplane which is here shown as ofthe bi-plane type, although it is obvious that the invention may beapplied to aeroplanes of other types. Fixed on the rearwardly extendinframe 2 of the aeroplane is a framewor body 3 and pivotally supported onthe central crossbar of tral bar of a substantially rectangular castingmember 4 to the rear bar of which are secured several verticalower-exerting springs 6, the lower ends 0 which are severtical detailsection 20.; Fig. 22 is a detail ack of the seat of the cured to therear crossarm' of the frame 3,

as shown in Fig. 2. The front cross arm edevice illustrated in Figs ofthe form of t 1 to 24 inclusive may .be denominated a catato bearagainst the underside of a parachute carrierconsisting preferabl of ahickory-bar 8. The rear end of this ar passes under the rear cross bar 5of the catapult, whereby when the catapult is released, its sprin s 6will cast the parachute carrielg upwar ly into the air. The extremeforward end of member Sis connected by means of a rope '9 or otherflexible consame has been fullydetail section on line this frame work isthe con-- necting member to the catch lever 10 which is pivoted at 11 onthe frame 3. .The'front the carrier is released and the catapult ispermitted to cast the same.

Pivotally mounted on the carrier 8 is a bracket 14 (see Fig. 6) whichmay be adjusted vertically by means of a set screw 15, extending througha carrier member. Resting on this bracket is a parachute inclosing hoodwhich is preferably of metal and which comprises an upper solid domeshaed portion 16 perforated with air hole's an' a lower cylindrical portionconsisting of slats 17 which by means of hinges 18 connecting them tothe dome are adapted to swing outwardly to permit the free escape of theparachute therefrom. The object of the adjustable bracket is to permitthe hood to be set out at an inclined angle to the carrier so that whenthe latter is discharged the hood will be thrown rearwardly or forwardlyas desired whichever serves to more effectually clear the aeroplane. Tohold the slats of the hood in position, the lower ends thereof are setwithin a flange 19 of an annular plate 20 and hooked levers 21 areadapted to enter perforations in this flange and in opposite slats forthe purpose of hold ing the hood and the plate 20 locked together. Theselevers are pivoted on lugs 22 projecting from the under side of theplate 20. adapted to be held normally apart so as to keep. the u perends in engagement with the hub and ange bridge piece 23, to said armsserves to draw the lower ends together and thus releases the upper endsfrom the flange and hood when the bridge 23 has been withdrawn from itsengagement with the arms. A releasin cord 25 is connected to the bridgemem er and extends over a pulley 26 which is mounted on the parachutecarrier 8. The cord extends down through an aperture in this carrier andis fixed at its lower end to a Suitable eye on the frame 3. When thecarrier is thrown upwardly by the cata ult a tension will be exerted onthis cor 25 which will pull the spacing bridge 23 away from engagebymeans ofa releasable ment with the arms of the hooked members thuspermitting the release of the members from the hood.

Theplate 20 is perforated to permit the entrance of air thereto. Thisplate in con- 10 will be permitted to fly I The lower arms of the leversare while a spring 24 connected I (See Figs. 6 and 8).

pending the spring readily,

junction with the expanding hood constitutes the inclosing means for theparachute 27 which in Fig. 6 is shown as inclosed in the hood, theconnecting ropes thereof being shown as atthe bottom 0 the hood andresting on the plate 20.

Adapted to be releasably attached to the parachute at its throat is aparachute expanding member consisting of an annular sprin or series offiat springs laid together and esignated by the reference character 28.(See Figs. 5, 6, 8, 20and 21.) This spring member in expanded form isillus trated in Figs. 20 and 21. At intervals around the circumferenceare spring clips 29 which are adapted to loosely engage thecircumferential cord 30 attached to the parachute 27 at approximatelythe throat of the parachute. This expanding spring is of less diameterthan the parachute and is adapted to expand the throat of the parachuteoutwardly and upon the further distention of the parachute, owing to itscatching the air, the cord and released from the spring clips, thusdisengaging the parachute from the expanding spring.

The sprin member 28 is adapted to be confined wit in the inclosing hoodwith the slats of suchhood exerting a tension upon thespring so thatupon the release of the slats the spring will be permitted to expandcircumferentially. To this end this spring is bent into the form ofloops as shown in 5 and the inner ends of these loops are adapted to beinserted within and held by the walls of an annular groove 31 (see Figs.5, 6 and 8), formed in a ring 32 which is adapted to lie loosely withinthe hood, being held therein by the pressure of the springs. The outerends of the loops thus formed are adapted to be bent outwardly and heldin such upright bent position by the pressure of the slats 17 of thehood when these slats are'docked in closed position. When the slats arereleased these loops will first spring downwardly from an uprightpositin to a horizontal position and then the expanding force of thespring will uncoil the loops exuntil it assumes the form shown in Figs.20 and 19. The grooved ring 32 is preferably provided with a centralmesh body 33. The connecting cords 34 of the parachute 27 are attachedat their lower ends to a supporting rope 35. This rope is attached tothe aviator through a shoe absorbing member which comirises a back plate36 adapted to bear again and support the back of the aviator andprovided with a suitable attaching harness 37. The rope 35 is adapted toenter and lie in a convolute groove formed on a plate by ridges 38 in asuitable body with- 39 see 13. The rope-is ada ted to be held in $556grooves by means of frangible he supporting the belt which passesthrough the plate,

Fig. 11, or other connecting means 42 on the l this end the seat right aprojection 45 extending into line with a pin 45' on the seat. A spring47 tends to throw the rod 46 to the right, looking Fig. 10, so as torelease said rod 46 whereby the back plate is steadied and held inupright position. A pivoted trigger 50 is mounted on the back of theplate 36 and the supporting rope 35 is adapted to be detachably orbreakably tied to this trigger piece of twine 51. The trigger engages anotch in the rod 46 and thereby serves to hold the rod fromdisengagement with the ears on the seat against the pressure of thespring 47. 11 car 46' on the rod braces the trigger. When the parachutehas been discharged and the supporting rope 35 is tautened, it will liftthe and supporting rope 48.

To guide the aviator as he is separated from the aeroplane and toprevent him from coming in contact with the frame of the machine, abackwardly inclined wire guard frame 52 is provided (See Fig. 15 andFig. 4). This guard frame is mounted buhind the seat of the aviator andslants u wardly and rearwardly so that should h e be. drawn backwardlyfrom the aeroplane, he will be guarded against commg in com tact withthe frame work of the machine to his rear.

In order to adjust the tension of the springs 6 which are adapted tothrow the e rear cross rod of the frame 6 is made rotatably adjustablein its sockets of the springs are fastened to ropes which are coiledaround the same. Both ends of this cross rod may be provided withratchets 53, adapted to be engaged by The'operation of the device abovedescribed is as follows :-Upon the destruction force of the springs 6-will pull down the rear end of the catapult 4, forcibly throwing up thefront end and thus casting the parachute carrier upwardly andrearwardly, y the carrier on the rope 25 will release the bridgepermitting the spring 24 to raw the outer ends of the hooks 21 towardone another, thereby disconnecting the plate 20 from the hood, (1unlocking the hood.

he hood rests loosely on the bracket 14 and w en the carrier is throwninto the air, will also be thrown from the bracket and carrier by thepropulsive force of the carrier. The plate 20 is connected only to thehood and this connection is solely through the hooks 21, hence when thecarrier is cast into the air, the plate 20 will The hinged slats of thehood when thus released from the plat 20 are forced outwardly by thedownward movement of the loops of the spring member 28, thus opening thehood and facilitating its separation from the parachute inclosedthereby. The separation of the quicke spring.

of the parachute from the t e discharge aeroplane 18 shown 1n Fig. 19 inwhich it will appear that the expanding spring, the hood and thesupporting ring are all immediately se arated from t e parachute uponthe di arge of these parts from the aeroplane. As the supporting ropebecomes taut, owing to the filling with air, it will release or raisethe tri ger 50, permitting the separation of the ack from the seat inthe manner heretofore described and the supporting rope will thengradually break the shock absorbingfwines 40 until the rope has unwoundand rought up against its fastening means 42, Whereupon the aviator willbe suspended as shown in Fig. 14.

In Fig. 25 is shown the modification of the means of casting theparachute into the air. In this form of the device a frame 57 mounted onthe aeroplane is provided and a movable frame or catapult member 58 ismounted on this fixed frame with .its rear end pivoted thereon and itsfront end movable. -The front rod of this front frame extends under theparachute carrier member 59. The rear end'of the member 59 extends underthe rear end of the frame 57. The front arm of the movable frame 58bears upon the upper end of a piston rod 60 carried by a piston 61movable in a cylinder 62. This cylinder is connected by means of a pipe63 to a vessel 64 adapted to contain compressed air or other gas underpressure. A cock 65. controls this pipe 63 and a releasing rope 66 isconnected to this cock and a apted to open the same to permit the rushof the as under pressure to the cylinder. By this construction it willbe seen that by the admission of a charge of gas under pressure to thecylinder that the iston thereof will be forced upwardly t us forciblydriving upward the front end of the frame 58 and thereby casting theparachute carrier 59 and the parachute upwardly and rearwardly.

In Figs. 27 to 30 inclusive, there is shown another modified form-of thepower means for casting the parachute. In this arrangement an expandinghood 67 of substantially the same construction as that shown in thedevice first described is employed and the parachute is containedtherein. The bottom plate 68 with which this hood engages and whichcorresponds to plate 20 of the device of Fig. 1 is fixed to a pistonmember 69, consisting of a long solid cylinder which fits within ahollow cylinder 70 and is adalpted to rest upon or near a charge of power or other explosive 71, in the bottom of the cylinder 70. A primer 72is adapted to fire this charge of explosive and this primer is ignitedby a percussion hammer 3 which is controlled by a trigger 74, connectedto a pull cord 75 the aviator. In this arrangement when the aviatorpulls the cord 75 the explosive charge of the parachute withinconvenient reach of.

within the cylinder 70 will be tiploded, thus discharging the istoncylinder 69 and the hood carried there y.

Having thus described my invention what I claim is 2-- 1. In anaeronautical safety device, in

combination with a parachute and an inclosing member therefor to confinethe parachute and hold it' folded, releasable means to lock theinclosing means, a supporting member for the inclosing means detachablymounted on the aeroplane and power means operable to exert force uponthe supporting member for casting the same from the aeroplane uponactuation thereof, substantially as described. y

2. In an aeronautical safety device, in combination with a parachute,inclosing means therefor, carrying means for said inclosing means, alever for casting said carrying means from the aeroplane, said leversupporting said carrying means at one end thereof away from theaeroplane, power means attached to and adapted to operate said lever andmeans controlled by the aviator for releasin said power means,substantially as descri ed.

3. In an aeronautical safety device, in combination with a parachute, aninclosing hood therefor having a continuous portion at one end thereofadapted to receive the upper end of the parachute,said hood havingoutwardly and circumferentially expanding portions at the other endthereof operable to suddenly release the parachute, spring means bearingagainst the free extremities of said portions to positively expand thesame, means for holding said portions closed and means for releasinholding means, substantially as descri ed.

4. In an aeronautical safety device, in combination with a. parachute aninclosing hood therefor comprisin a body portion forming one end of the00d and pivoted slats forming the side of the hood, means to hold saidslats closed and means to release said holding means, substantially asdescribed. V 5. In an aeronautical safety device, in combination with aparachute, a parachute expanding spring, means to confine said parachuteand sprin within a limited space, means to release said confining meansand automatically detachable connections between said parachute andexpanding spring, substantially as described. Y

6. In an aeronautical safety device, in combination with a parachute, anexpanding spring of less diameter than the parachute clips .on saidspring adapted to detachably engage the lower border of said parachute,means within which said parasaid chute and spring are confined, saidmeans means to release said confining means, substantially as described.

an aeronautical safety device,,in combination with a parachute, aslatted hood for containing said parachute, means engaging the ends ofsaid slats, hooked arms operable to hold said slats and means together,means to exert pressure on said arms to hold them in operative positionand means to release them from the slats, substantially as described. 7

8. In an aeronautical safety device, in combination with a parachute,suporting means for said parachute mounte on the aeroplane, means forautomatically casting said parachute from the aeroplane and a guardmember placed to the rear of the aviator to guard him in his separationfrom the aeroplane, substantially as described.

9. In an aeronautical safety device, in

combination with a Earachute, a seathand a attac ed to member forreleasing said back from-tho seat as the connecting member becomes tautwhen the parachute is cast free from the aeroplane.

In witness whereof, my hand and seal at Lexington, Fayette county,Kentucky, June, A. D; nineteen hundred and thirteen.

80L0ll0R nan VAN mama Ja. [a a3 Witnesses:

3o I have hereunto set-

